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  • STRUCTURAL MECHANICS  (182)
  • 1975-1979  (182)
  • 1955-1959
  • 1945-1949
  • 1
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    Stability analysis of nonlinear autonomous systems - General theory and application to flutter (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The analysis makes use of a singular perturbation method, the multiple time scaling. Concepts of stable and unstable limit cycles are introduced. The solution is obtained in the form of an asymptotic expansion. Numerical results are presented for the nonlinear flutter of panels and airfoils in supersonic flow. The approach used is an extension of a method for analyzing nonlinear panel flutter reported by Morino (1969).
    Keywords: STRUCTURAL MECHANICS
    Type: AIAA PAPER 75-102 , American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting; Jan 20, 1975 - Jan 22, 1975; Pasadena, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    High heat flux actively cooled honeycomb sandwich structural panel for a hypersonic aircraft (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The results of a program to design and fabricate an unshielded actively cooled structural panel for a hypersonic aircraft are presented. The design is an all-aluminum honeycomb sandwich with embedded cooling passages soldered to the inside of the outer moldline skin. The overall finding is that an actively cooled structure appears feasible for application on a hypersonic aircraft, but the fabrication process is complex and some material and manufacturing technology developments are required. Results from the program are summarized and supporting details are presented.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-2959
    Format: application/pdf
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  • 3
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    Tests of beaded and tubular structural panels (1978)
    In:  CASI
    Details
    Publication Date: 2006-06-12
    Description: Two efficient concepts built from curved elements were identified, and a data base for tubular panels was developed. The tubular panel failure modes were understood, and the data base for these panels indicated that their performance can be predicted. The concepts are currently being tested in a realistic builtup structure; 157 room temperature tests and 67 hot tests were made with no structural failures, although all of these tests were not at the design load of the structure.
    Keywords: STRUCTURAL MECHANICS
    Type: Recent Advan. in Structures for Hypersonic Flight, Pt. 2; p 538-576
    Format: text
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  • 4
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    The automated multi-stage substructuring system for NASTRAN (1975)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The substructuring capability developed for eventual installation in Level 16 is now operational in a test version of NASTRAN. Its features are summarized. These include the user-oriented, Case Control type control language, the automated multi-stage matrix processing, the independent direct access data storage facilities, and the static and normal modes solution capabilities. A complete problem analysis sequence is presented with card-by-card description of the user input.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Res. Center NASTRAN: Users' Experiences; p 571-591
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  • 5
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    NASTRAN applications to aircraft propulsion systems (1975)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The use of NASTRAN in propulsion system structural integration analysis is described. Computer support programs for modeling, substructuring, and plotting analysis results are discussed. Requirements on interface information and data exchange by participants in a NASTRAN substructure analysis are given. Static and normal modes vibration analysis results are given with comparison to test and other analytical results.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Res. Center NASTRAN: Users' Experiences; p 91-104
    Format: application/pdf
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  • 6
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    Implementation on a nonlinear concrete cracking algorithm in NASTRAN (1976)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A computer code for the analysis of reinforced concrete structures was developed using NASTRAN as a basis. Nonlinear iteration procedures were developed for obtaining solutions with a wide variety of loading sequences. A direct access file system was used to save results at each load step to restart within the solution module for further analysis. A multi-nested looping capability was implemented to control the iterations and change the loads. The basis for the analysis is a set of mutli-layer plate elements which allow local definition of materials and cracking properties.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Ames Res. Center NASTRAN: User's Experiences; p 479-494
    Format: application/pdf
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  • 7
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    Loadcell supports for a dynamic force plate (1975)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: An apparatus was developed to accurately measure components of force along three mutually perpendicular axes, torque, and the center of pressure imposed by the foot of a subject walking over its surface. The data obtained were used to supplement high-speed motion picture and electromyographic (EMG) data for in-depth studies of normal or abnormal human gait. Significant features of the design (in particular, the mechanisms used to support the loadcell transducers) are described. Results of the development program and typical data obtained with the device are presented and discussed.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Kennedy Space Center 9th Aerospace Mech. Symp.; p 265-280
    Format: application/pdf
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  • 8
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    A 3-D hydroelastic analysis in NASTRAN with general fluid and structure geometry (1977)
    In:  Other Sources
    Details
    Publication Date: 2016-06-07
    Description: The implementation of a general three dimensional hydroelastic mode analysis capability in NASTRAN is presented. Finite elements with polyhedral shapes define the fluid; existing NASTRAN plate elements define the fluid/structure interface. Efficient solution methods were implemented to allow a separate structural matrix reduction and to allow connection of the fluid mass directly to a small set of grid points or modal coordinates representing the structure. Test case results for the various solution options are presented.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA, Washington 6th NASTRAN (R) Users' Colloq.; p 3-23
    Format: text
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  • 9
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    Hypersonic structures: An aerodynamicist's perspective, or one man's dream is another man's nightmare (1978)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The relationship between hypersonic aerodynamic and structural design is reviewed. The evolution of the hypersonic vehicle design is presented. Propulsion systems, structural materials, and fuels are emphasized.
    Keywords: STRUCTURAL MECHANICS
    Type: Recent Advan. in Structures for Hypersonic Flight, Pt. 1; p 5-38
    Format: application/pdf
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  • 10
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    Design and fabrication of a radiative actively cooled honeycomb sandwich structural panel for a hypersonic aircraft (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The panel assembly consisted of an external thermal protection system (metallic heat shields and insulation blankets) and an aluminum honeycomb structure. The structure was cooled to temperature 442K (300 F) by circulating a 60/40 mass solution of ethylene glycol and water through dee shaped coolant tubes nested in the honeycomb and adhesively bonded to the outer skin. Rene'41 heat shields were designed to sustain 5000 cycles of a uniform pressure of + or - 6.89kPa (+ or - 1.0 psi) and aerodynamic heating conditions equivalent to 136 kW sq m (12 Btu sq ft sec) to a 422K (300 F) surface temperature. High temperature flexible insulation blankets were encased in stainless steel foil to protect them from moisture and other potential contaminates. The aluminum actively cooled honeycomb sandwich structural panel was designed to sustain 5000 cycles of cyclic in-plane loading of + or - 210 kN/m (+ or - 1200 lbf/in.) combined with a uniform panel pressure of + or - 6.89 kPa (?1.0 psi).
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-2957
    Format: application/pdf
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